WO2009048666A2 - Pylône de lancement et de récupération d'aéronef - Google Patents

Pylône de lancement et de récupération d'aéronef Download PDF

Info

Publication number
WO2009048666A2
WO2009048666A2 PCT/US2008/070598 US2008070598W WO2009048666A2 WO 2009048666 A2 WO2009048666 A2 WO 2009048666A2 US 2008070598 W US2008070598 W US 2008070598W WO 2009048666 A2 WO2009048666 A2 WO 2009048666A2
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
launch
child
recovery
pylon
Prior art date
Application number
PCT/US2008/070598
Other languages
English (en)
Other versions
WO2009048666A3 (fr
Inventor
Kevin Keaveney
Original Assignee
Kevin Keaveney
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Kevin Keaveney filed Critical Kevin Keaveney
Publication of WO2009048666A2 publication Critical patent/WO2009048666A2/fr
Publication of WO2009048666A3 publication Critical patent/WO2009048666A3/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/20—Launching, take-off or landing arrangements for releasing or capturing UAVs in flight by another aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U80/00—Transport or storage specially adapted for UAVs
    • B64U80/60—Transport or storage specially adapted for UAVs by wearable objects, e.g. garments or helmets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U80/00—Transport or storage specially adapted for UAVs
    • B64U80/80—Transport or storage specially adapted for UAVs by vehicles
    • B64U80/82—Airborne vehicles

Definitions

  • the present invention relates to the launch and recovery of a child aircraft from a parent aircraft, to include aerial refueling of the child aircraft.
  • the invention relates to the launch and recovery of a child aircraft from a parent aircraft, to include aerial refueling of the child aircraft.
  • This proven concept is not new for either manned or unmanned flight.
  • this air launch and recovery protocol can be broken down into three distinct categories:
  • Unmanned Aerial Vehicles launched from manned aircraft.
  • UAVs Unmanned Aerial Vehicles
  • Eliminate child aircraft forward basing o Eliminate or reduce child aircraft organizational infrastructure, o Eliminate visibility of child aircraft operations,
  • an Air Launch and Recovery Pylon (ALRP) does not require the child aircraft to have a payload bay with operable doors, nor pay loads in the form of cartridges.
  • ALRP Air Launch and Recovery Pylon
  • the ALRP eliminates the need to fly the child aircraft in an inverted manner to effectuate docking, undocking and/or refueling; and • Allows for the child aircraft to be carried below (in contrast to U.S. Patent No. 6,869,042 B2) and away from the parent aircraft (in contrast to U.S. Patent No. 6,540,179 B2), therein providing for a greater range of child aircraft types and shapes to be carried by the ALRP.
  • FIG 1 is a top and bottom view of a child aircraft and a parent aircraft combination
  • FIG 2 is an ALRP schematic
  • FIG 3 is a depiction of an Air Launch and Recovery Pylon Docking Section
  • FIG 4 is a depiction of the ALRPDS stabilizing arm location
  • FIG 5 is a depiction of an ALRP Docking Unit (ALRDSDU);
  • FIG 6 is a depiction of an ALRPDS and an ALRDSDU relationship
  • FIG 7 is a depiction of a Child Aircraft Docking Probe (CADP);
  • FIG 8 is a depiction of a child aircraft's ALRP points of interest
  • FIG 9 is a depiction of an ALRP refueling system
  • FIG 10 is a view of a jettisonable ALRS and child aircraft
  • FIG 11 is a flow diagram of an ALRP operating sequence
  • FIG 12 is layout 1 for a large capacity aircraft (i.e. jumbo passenger aircraft), along with an associated ALRP operating sequence
  • FIG 13 is layout 2 for a large capacity aircraft (i.e. jumbo passenger aircraft), along with an associated ALRP operating sequence
  • FIG 14 is layout 3 for a large capacity aircraft (i.e. stealth bomber aircraft), along with an associated ALRP operating sequence.
  • FIG. 1 is a top 20 and bottom 22 view of the docked unmanned aircraft, otherwise referred to as a child aircraft 24, and a manned aircraft, referred to as a parent aircraft 26.
  • the two are connected by the ALRP 28.
  • the parent aircraft is capable of takeoff and landing with the child aircraft 24 attached.
  • the child aircraft 24 is flown in a normal flight profile with no unnatural flight maneuvers, such as inverted flights, to launch, recover or refuel from the parent aircraft.
  • An unmanned child aircraft 24, and a manned parent aircraft 26 are not the only embodiment of this invention.
  • the invention is a method for launching and recovering a child aircraft, manned or unmanned, for continuous flight to and from a manned or unmanned parent aircraft, airship or helicopter, mounting the ALRP to affect the launch, recovery and refueling of said child aircraft.
  • FIG. 2 is an ALRP schematic. There are two primary sections: an upper section, known as the Upper ALRP (UALRP) 30, and a lower section, known as the ALRP Docking Arm (ARLPDA) 44.
  • ALRP Upper ALRP
  • ARLPDA ALRP Docking Arm
  • the UALRP 30 contains eight primary elements: a UALRP data link antenna, wire harness (includes an optional hard wiring connection to the parent aircraft) 32, a UALRP motor 34, a UALRP power source (includes an optional connection to the aircraft power source) 36, a UALRP child aircraft fuel tank (includes an optional connection to the aircraft fuel system) 38, a UALRP telescopic fuel hose 40, an UALRP hinged panel 41 and a UALRP parachute chamber 42 containing two parachutes with lanyards.
  • the UALRP data link antenna, wire harness 32 and related equipment on both the parent aircraft 26 and the child aircraft 24 serve to transmit control signals to and from the parent aircraft 26 to both the ALRP 28 and the child aircraft 24.
  • this is effectuated through hard wiring or electronic signals via a data link, facilitated by antennas on both the parent aircraft and the pylon.
  • the same method of signal transmission is true in regard to the child aircraft 24 with a distinct difference.
  • the ALRPDA 44 contains two primary elements: an ALRPDA piston 46 and an
  • ALRPDA piston 46 consists of varying numbers of extension elements 47.
  • the number of extension elements 47 is dependent upon the parent aircraft's 26 design parameters.
  • the purpose of the ALRPDA 44 is to stabilize the child aircraft 24 in the vertical axis.
  • FIG. 3 is a depiction of the ALRPDS 48 showing five elements: the
  • ALRPDS/ALRPDA connecting point 50 the ALPDS stabilizing piston (right) 52, stabilizing piston locking pin (right) 56, the ALPDS stabilizing piston (left) 54 and stabilizing piston locking pin (left) 58.
  • the ALRPDS stabilizing pistons 52 and 54 when not connected to a child aircraft, have a stowed position 53 against the ALPDS 48. To connect to a child aircraft 24, the ALPDS stabilizing pistons 52 and 54 rotate and drop away from the ALRPDS 48 to a deployed position 55.
  • the primary purpose of the ALRPDS stabilizing pistons 52 and 54 in the deployed position 55 is to stabilize the child aircraft 24 in the longitudinal and lateral axes.
  • the secondary purpose, if necessary, of the ALRPDS stabilizing pistons 52 and 54 in the deployed position 55 is to act as a wing folding mechanism for the child aircraft 24 by pivoting around the stabilizing piston locking pins 56 and 58 and partially retracting toward the ALRP
  • FIG. 4 is a front 21 and side 23 diagram of an alternative placement for the
  • the ALRPDS stabilizing pistons 52 and 54 are relocated from the ALRPDS 48 to the ALRPDA piston 46.
  • the purpose of the alternate placement of the stabilizing pistons 52 and 54 behind the ALRPDS 48 is to provide greater lateral stability to larger child aircraft 24 than is possible in the ALRPDS location. This is effectuated by increasing the distance between the ALRPDS stabilizing pistons 52 and 54 and the ALRPDS 76, as illustrated in 57 and 59.
  • the ALRPDS stabilizing pistons 52 and 54 are attached to the ALRPDA piston
  • an ALRPDS slide restrictor 60 is located above the ALRPDS cuff 62 on the middle extension element of the
  • FIG 5 is a depiction of the ALRP Docking Unit (ALRPDU) 64.
  • the ALRPDU consists of five elements: a primary camera 66, a secondary camera 68, a laser-guided docking system 70, a vertical locking pin 72 and a CADP locking receptor 74.
  • FIG 6 is a relationship diagram of the ALRPDS 48 and the ALRPDU 64.
  • ALRPDU 73 is mounted within the ALRPDS 48.
  • the ALRPDU 64 and the ALRPDS 48, now acting as one element, can rotate down 45 degrees 75 at the ALRPDS/ALRPDA connecting point 50.
  • FIG 7 is a depiction of the CADP 76.
  • the CADP consists of four elements: a
  • CADP 45° camera 78 a CADP horizontal camera 80, a CADP laser-guided docking system
  • CADP 76 pivots on a single axis 86 to align the CADP with the downward rotated ALRPDS 48.
  • the CADP 76 because of its long flat side design, like that of the ALRPDU 64, gives added strength to the CADP's horizontal locking pin 84 connection with the ALRPDU's CADP horizontal locking pin receptor 74.
  • FIG 8 is a depiction of the child aircraft's ALRP points of interest. There are four [five?] points of interest: the CADP 76, the child aircraft's vertical locking pin receptors
  • the child aircraft's parachute anchor point 90 the child aircraft's parachute anchor point 90, the child aircraft's refueling point 92 and the child aircraft's data connection point 93.
  • FIG 8 is a depiction of the child aircraft's ALRP points of interest. There are four [five?] points of interest: the CADP 76, the child aircraft's vertical locking pin receptors
  • the child aircraft's parachute anchor point 90 the child aircraft's parachute anchor point 90, the child aircraft's refueling point 92 and the child aircraft's data connection point 93.
  • the CADP 76 location is determined during the design or modification of the child aircraft 24 to accommodate the design of the ALRP 28.
  • the child aircraft's vertical locking pin receptors 88 are where the ALRPDS stabilizing piston locking pins 56 and 58 and
  • the child aircraft's parachute anchor 90 provides a location to attach the ALRP parachute lanyard (part of the parachute located in the ALRP parachute chamber 42).
  • the child aircraft's refueling receptor 92 is where the UALRP's fuel quick release valve 98 inserts into the child aircraft 24.
  • the child aircraft's data connection point 93 is where the UALRP data link and wiring harness 32 insert into the child aircraft 24.
  • FIG 9 is a depiction of the UALRP's refueling system and operating sequence.
  • the UALRP's fuel tank 38 the UALRP's telescopic fuel hose 40, the UALRP' s optional parent aircraft fuel connector 94, an UALRP accordion flex section of the telescopic fuel hose 96, an UALRP telescopic fuel hose extension mechanism 100 and an UALRP fuel quick release valve 98.
  • the UALRP's fuel tank 38 runs almost the entire length of the pylon. At the top of the fuel tank is the UALRP's optional parent aircraft fuel connector 94, which is used to connect to the parent aircraft's fuel system. Below the fuel tank is a UALRP's telescopic fuel hose 40. At the bottom of the UALRP's telescopic fuel hose 40 is the UALRP's accordion flex section of the telescopic fuel hose 96, which is powered by a UALRP telescopic fuel hose extension mechanism 100. At the tip of the UALRP's accordion flex section of the telescopic fuel hose 96 is the UALRP's fuel quick release valve 98.
  • the operation sequence of the UALRP's refueling system is simple.
  • the child aircraft operator will manually engage the refueling system. This will activate the UALRP's telescopic fuel hose extension mechanism 100, which stretches the UALRP's accordion flex section of the telescopic fuel hose 96 and inserts a quick release valve 98 into the child aircraft's refueling point 92.
  • the fuel is dispensed from the UALRP's fuel tank 38 into the child aircraft 24.
  • the child aircraft operator Upon completion of the refueling, indicated through sensors onboard the child aircraft 24 and the parent aircraft 26, the child aircraft operator will manually disengage the refueling system.
  • the quick release valve 98 releases from the child aircraft.
  • the UALRP's telescopic fuel hose extension mechanism 100 reverses, and the accordion flex section 96 of the telescopic fuel hose retracts into a stowed position within the UALRP.
  • the UALRP data link, wiring harness 32 can piggy back on the UALRP telescopic fuel hose extension mechanism, to plug into the child aircraft 24 when the child aircraft 24 is in the ALRP 28 stowed position.
  • FIG 10 is a view of the jettisonable child aircraft 24 and the ALRP 28. They are jettisonable to counter any asymmetrical flight conditions the parent aircraft may encounter in either a threat or non-threat environment.
  • the child aircraft 24 and/or the ALRP 28 free fall to the ground without the benefit of a parachute.
  • the intent is for gravity to destroy the child aircraft
  • the child aircraft 24 and/or the ALRP 28 descend to the ground on their own respective parachutes.
  • the purpose of the parachutes is to slow the rate of descent sufficiently to allow recovery and re-use of all or part of the jettisoned items.
  • the parachutes for the child aircraft 24 and the ALRP 28 reside in a parachute chamber 42 in the upper ALRP 30. Each parachute is attached to its respective element by a static line. Note that the child aircraft 24 relies upon a parachute residing in the upper ALRP
  • FIG. 11 is a flow diagram of a generalized seven-step ALRP operating sequence.
  • Step 1 102 the ALRPDA 44 moves from a stowed position to an extended position using motors and sensors.
  • Step 2 104 the child aircraft 24 arrives at its rendezvous position below and behind the deployed ALRPDA 44 using an autonomous air refueling system and associated procedures.
  • Step 3 106 by using motors and sensors, the ALRPDS 48 prepares to receive the child aircraft 24 by rotating down to a 45° angle to align with the child aircraft's position 106.
  • the child aircraft 24 operator visually identifies the parent aircraft 26 through the CADP' s 45° (up) video camera 78.
  • the child aircraft 24 controller manipulates the child aircraft 24 through flight control inputs so the child aircraft aligns with the ALRPDS 48.
  • the UAV operator rotates the CADP 76 45° and shifts visual to the CADP 's horizontal video camera 80 and laser-guided docking system (crosshair type) 82 mounted in the tip of the CADP.
  • the child aircraft 24 controller applies power to the child aircraft and begins a 45° horizontal climb.
  • the child aircraft 24 operator increases child aircraft speed to eliminate distance between the child aircraft and the ALRPDS 48.
  • Step 5 110 the child aircraft 24 then docks with the ALRPDS 48.
  • the CADP' s horizontal locking pin 84 engages the ALPDU 's horizontal locking pin receptor 74.
  • the ALRPDS 48 and the CADP 76 rotate to the horizontal position to align the parent aircraft 26 and the child aircraft 24 in parallel.
  • the ALRPDS stabilizing pistons 52 and 54 swing away from the ALRPDS 48 by rotating and depressing to touch the child aircraft's wings.
  • the child aircraft 24 is now stabilized in the longitudinal, lateral and vertical axes, allowing it smooth airflow, given its intrinsic distance from the parent aircraft 26.
  • Step 7 114 using motors and sensors, the ALRPDA 44 retracts from its extended position to a stowed position, always keeping the child aircraft 24 in a horizontal position.
  • FIG. 12 is layout 1 for a large capacity parent aircraft 26 (i.e. jumbo passenger aircraft), along with a more generalized six-step ALRP operating sequence than found in FIG 11.
  • a parent aircraft consists of an overhead, or second deck 122, a main deck 124, a forward cargo hold 126 and a rear cargo hold 128. Added to the rear cargo hold 128 are upper 130 and lower 132 doors.
  • the overhead, or second deck 122 acts as a manning and equipment area.
  • the main deck 124 is the child aircraft's hanger and armament area.
  • the forward cargo hold 126 serves as a command and control area.
  • the rear cargo hold 128 contains the ALRP and is the child aircraft's launch area.
  • the bottom half of the diagram shows a generalized six-step ALRP operating sequence.
  • Step 1 136 the sequence starts with the vertical insertion (lowering) of the child aircraft 24 into the rear cargo hold 128.
  • Step 2 138 once the child aircraft 24 is in position, the ALRPDA 44 extends through the UALRP' s hinged panel 41 in the front of the ALRP 28 and docks with the child aircraft 24.
  • Step 3 140 the ALRPDS's stabilizing pistons 52 and 54 deploy to allow the ALRPDS 28 to bear the child aircraft's full weight.
  • Step 4 142 as the ALRDA 44 starts to move back to its stowed position, the child aircraft's suspension system, (no longer needed to hold the child aircraft 24), retracts into the main deck 124 area, and the rear cargo hold's upper doors 130 close.
  • Step 5 144 the rear cargo hold's lower doors open 132, and the ALRPDA 44 extends.
  • Step 6 146 once the ALRPDA 44 is in the fully extended position, the child aircraft 24 separates from the ALRPDS 48. The ALRPDA 44 retracts to the stowed position, and the rear cargo hold's lower doors 132 close.
  • FIG. 13 is layout 2 for a large capacity parent aircraft 26 (i.e. jumbo passenger aircraft), along with a more generalized six-step ALRP operating sequence than found in FIG 11.
  • the top right half of the diagram shows the cross section 118 and the side section
  • Such a parent aircraft consists of an overhead, or second deck 122, a main deck 124, a forward cargo hold 126 and a rear cargo hold 128.
  • layout 1 There are two differences between layout 1 and layout 2.
  • the first difference is that in layout 2 the rear cargo hold 128 extends to the top of the main deck 124.
  • the rear cargo hold's upper doors 130 are relocated to the upper forward section of the rear cargo hold in order to provide access to the main deck 124.
  • the rear cargo hold's lower doors 132 are at the same location as described in layout 1.
  • the overhead, or second deck 122 acts as a manning and equipment area.
  • the main deck 124 is the child aircraft's hanger and armament area.
  • the forward cargo hold 126 serves as a command and control area.
  • the rear cargo hold 128 contains the ALRP and is the child aircraft's launch area.
  • top left half and bottom half of the diagram show a generalized six-step
  • Step 1 148 the sequence starts with the horizontal insertion of the child aircraft 24 into the rear cargo hold 128.
  • Step 2 138 once the child aircraft 24 is in position, the ALRPDA 44 extends through the UALRP's hinged panel 41 in the front of the ALRP 28 and docks with the child aircraft 24.
  • Step 3 140 the ALRPDS 's stabilizing pistons 52 and 54 deploy to allow the ALRPDS 28 to bear the child aircraft's full weight.
  • Step 4 142 as the ALRDA 44 starts to move back to its stowed position, the child aircraft's suspension system, (no longer needed to hold the child aircraft 24), retracts into the main deck 124 area, and the rear cargo hold's upper doors 130, now at the forward top position of the rear cargo hold 128, close.
  • Step 5 144 the rear cargo hold's lower doors open 132, and the ALRPDA 44 extends.
  • the second difference between layout 1 and layout 2 is that in layout 2 the ALRP 28 may be wider to allow more extension elements 47 to the ALRPDA piston 46.
  • the addition of extension elements to the ALRPDA piston 46 allows the ALRPDA 44 to cover the now greater distance 129 from the bottom of the ALRP 28 to the bottom of the rear cargo hold 128.
  • the ALRPDA 44 maintains the distance 131 between the ALRPDS 48 and the bottom of the parent aircraft 26, which creates the safest possible environment for the launch and recovery of the child aircraft 24.
  • Step 6 146 once the ALRPDA 44 is in the fully extended position, the child aircraft 24 separates from the ALRPDS 48. The ALRPDA 44 retracts to the stowed position, and the rear cargo hold's lower doors 132 close.
  • FIG. 14 is layout 3 for a large capacity parent aircraft 26 (i.e. stealth bomber aircraft), along with a more generalized three-step ALRP operating sequence than found in
  • FIG. 1 A first figure.
  • the top half of the diagram shows the cross section 118 and the side section 120 of a large capacity aircraft.
  • a parent aircraft consists of bomb bays 134 and bomb bay doors 136.
  • the bomb bays 134 contain the ALRPs 28 and act as the child aircraft's launch area.
  • Step 1 160 the bomb bay doors open with the ALRPDA 44 and child aircraft in the stowed position.
  • Step 2 162 the ALRPDA 44 extends.
  • Step 3 164 once the ALRPDA 44 is in the fully extended position, the child aircraft 24 separates from the ALRPDS 48.
  • ALRPDA 44 retracts to the stowed position, and the bomb bay doors 132 close.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Transportation (AREA)
  • Mechanical Engineering (AREA)
  • Electric Cable Installation (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

L'invention concerne un procédé pour lancer et récupérer un aéronef enfant avec ou sans pilote ainsi qu'un procédé permettant un vol continu vers un aéronef parent avec pilote ou sans pilote ou à partir de ce dernier, à partir d'un pylône qui est monté à l'extérieur ou à l'intérieur de l'aéronef parent. La mécanique du pylône est contenue dans le pylône et commandée à partir de l'aéronef parent, par l'intermédiaire d'un câble ou de signaux électroniques via une liaison de données facilitée par des antennes disposées sur l'aéronef parent et le pylône.
PCT/US2008/070598 2007-07-20 2008-07-21 Pylône de lancement et de récupération d'aéronef WO2009048666A2 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US96151907P 2007-07-20 2007-07-20
US60/961,519 2007-07-20
US17643608A 2008-07-21 2008-07-21
US12/176,436 2008-07-21

Publications (2)

Publication Number Publication Date
WO2009048666A2 true WO2009048666A2 (fr) 2009-04-16
WO2009048666A3 WO2009048666A3 (fr) 2010-01-07

Family

ID=40549792

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2008/070598 WO2009048666A2 (fr) 2007-07-20 2008-07-21 Pylône de lancement et de récupération d'aéronef

Country Status (1)

Country Link
WO (1) WO2009048666A2 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10081421B2 (en) 2015-03-26 2018-09-25 University Of North Dakota Perching attachment for unmanned aircraft
US10189565B2 (en) 2016-12-02 2019-01-29 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Modular unmanned aerial system with multi-mode propulsion
WO2020055374A1 (fr) 2018-09-10 2020-03-19 Oleksandr Volodymyrovych Stepura Plateforme de lancement et de récupération entièrement automatisée pour véhicule aérien sans pilote
CN113386962A (zh) * 2021-07-13 2021-09-14 北京航空航天大学 一种可空中释放回收的子母式无人机系统
CN113815887A (zh) * 2021-11-03 2021-12-21 沈阳天晴航空航天科技有限公司 一种快速空中发射箱装置

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106741939B (zh) * 2016-11-28 2018-11-13 南京信息工程大学 一种多旋翼无人机子母机系统及其控制方法

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3361377A (en) * 1965-12-30 1968-01-02 Melpar Inc Extendible-retractable boom
US5740985A (en) * 1996-09-16 1998-04-21 Scott; Harry Low earth orbit payload launch system
US6705573B2 (en) * 1999-12-30 2004-03-16 Advanced Aerospace Technologies, Inc. Survivability and mission flexibility enhancements for reconnaissance aircraft
US6869042B2 (en) * 2001-03-21 2005-03-22 Bae System Plc System for airborne launch of an aircraft from a larger carrier aircraft
US6889123B2 (en) * 2003-08-08 2005-05-03 The Boeing Company System and method for target tracking and navigation to a target
US20050204910A1 (en) * 2002-05-21 2005-09-22 Nir Padan System and method for enhancing the payload capacity, carriage efficiency, and adaptive flexibility of external stores mounted on an aerial vehicle
US7097137B2 (en) * 1999-07-23 2006-08-29 Advanced Aerospace Technologies, Inc. Launch and recovery system for unmanned aerial vehicles

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3361377A (en) * 1965-12-30 1968-01-02 Melpar Inc Extendible-retractable boom
US5740985A (en) * 1996-09-16 1998-04-21 Scott; Harry Low earth orbit payload launch system
US7097137B2 (en) * 1999-07-23 2006-08-29 Advanced Aerospace Technologies, Inc. Launch and recovery system for unmanned aerial vehicles
US6705573B2 (en) * 1999-12-30 2004-03-16 Advanced Aerospace Technologies, Inc. Survivability and mission flexibility enhancements for reconnaissance aircraft
US6869042B2 (en) * 2001-03-21 2005-03-22 Bae System Plc System for airborne launch of an aircraft from a larger carrier aircraft
US20050204910A1 (en) * 2002-05-21 2005-09-22 Nir Padan System and method for enhancing the payload capacity, carriage efficiency, and adaptive flexibility of external stores mounted on an aerial vehicle
US6889123B2 (en) * 2003-08-08 2005-05-03 The Boeing Company System and method for target tracking and navigation to a target

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
JONES ET AL.: 'UNMANNED AERIAL VEHICLES (UAVS) AN ASSESSMENT OF HISTORICAL OPERATIONS AND FUTURE POSSIBILITIE' THESIS, [Online] March 1997, Retrieved from the Internet: <URL:http://www.fas.orhttp://www.fas.org/irp/program/collecVdocs/97-0230D.pdf> [retrieved on 2009-04-03] *
SECRETARY OF DEFENSE: 'UNMANNED AERIAL VEHICLES ROADMAP' REPORT, [Online] December 2002, Retrieved from the Internet: <URL:http://www.milnet.com/archives/uav_roadmap.pdf> [retrieved on 2009-04-03] *

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10081421B2 (en) 2015-03-26 2018-09-25 University Of North Dakota Perching attachment for unmanned aircraft
US10189565B2 (en) 2016-12-02 2019-01-29 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Modular unmanned aerial system with multi-mode propulsion
WO2020055374A1 (fr) 2018-09-10 2020-03-19 Oleksandr Volodymyrovych Stepura Plateforme de lancement et de récupération entièrement automatisée pour véhicule aérien sans pilote
CN113386962A (zh) * 2021-07-13 2021-09-14 北京航空航天大学 一种可空中释放回收的子母式无人机系统
CN113815887A (zh) * 2021-11-03 2021-12-21 沈阳天晴航空航天科技有限公司 一种快速空中发射箱装置

Also Published As

Publication number Publication date
WO2009048666A3 (fr) 2010-01-07

Similar Documents

Publication Publication Date Title
US20210371081A1 (en) Air-Launched Unmanned Aerial Vehicle
US10589859B2 (en) Apparatus and method for aerial recovery of an unmanned aerial vehicle
US7946530B1 (en) Modular adaptive configured helicopter
US10696419B2 (en) Helicopter-mediated system and method for launching and retrieving an aircraft
EP1919774B1 (fr) Procedes et appareil pour systemes aeroportes
EP1370461B1 (fr) Systeme de lancement d&#39;aeronef aeroporte a partir d&#39;un aeronef lanceur plus grand
US9738383B2 (en) Remote controlled aerial reconnaissance vehicle
US10144511B2 (en) Helicopter-mediated system and method for launching and retrieving an aircraft
US6817573B2 (en) Aircraft
US20030136874A1 (en) Method for safer mid-air refueling
US10549850B1 (en) Portable multithruster unmanned aircraft
ES2881673T3 (es) Procedimientos y sistemas para el abastecimiento de combustible en vuelo de aviones
WO2016167849A1 (fr) Système et procédé faisant intervenir un hélicoptère pour le lancement et la récupération d&#39;un aéronef
WO2009048666A2 (fr) Pylône de lancement et de récupération d&#39;aéronef
EP1827972B1 (fr) Procede et dispositif d&#39;atterrissage d&#39;aeronef
EP4046912B1 (fr) Système de récupération d&#39;un carénage d&#39;une fusée et procédé de récupération correspondant
US4040583A (en) Methods and apparatus for effecting recovery of a high speed aircraft from a condition of incipient or developed spin
RU2748623C1 (ru) Малогабаритная беспилотная авиационная система
RU2456211C1 (ru) Беспилотный летательный аппарат с парашютной системой посадки

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 08838273

Country of ref document: EP

Kind code of ref document: A2

NENP Non-entry into the national phase

Ref country code: DE

32PN Ep: public notification in the ep bulletin as address of the adressee cannot be established

Free format text: NOTING OF LOSS OF RIGHTS PURSUANT TO RULE 112(1) EPC (EPO FORM 1205A DATED 11/05/2010)

122 Ep: pct application non-entry in european phase

Ref document number: 08838273

Country of ref document: EP

Kind code of ref document: A2